Multi-stage toy missile



May 26, 1964 1'. BOSWELL 3, ,1

MULTI-STAGE TOY MISSILE Filed Aug. 1, 1962 2 Sheets-Sheet 1 4 INVENTOR GEORGE T. BOSWELL May26, 1964 T. BOSWELL MULTI-STAGE TOY MISSILE 2 Sheets-Sheet 2 Filed Aug. 1, 1962 INVENTOR GEORGE T. BOSWELL BY W, M ATTORNEY United States Patent 3,134,194 MULTI-STAGE-TOY MISSILE George Thomas Boswell, 6710 Kenmont Place, Springfield, Va.

Filed Aug. 1, 1962, Ser. No. 214,049 9 Claims. (Cl. 46-74) This invention relates generally to elastically propelled multi-stage toy projectiles. The invention relates more particularly to toy projectiles of the multi-stage variety 1n which the successive stages are separated in a unique and realistic manner.

The prior art is replete with projectiles of the aforesaid variety which simulate full scale rocket and pay load separation or ejection and which, through a variety of means, operate to actuate a successive stage or stages upon the elapse of a pre-determined period of time or the happening of a certain event. Some of the latter type, for example, have means to sense the change of direction of the force of gravity with respect to the components of the missile due to the change of direction of the missile with respect to the earth as it passes through the maximum point of its trajectory and points downward for return. Many other ingenious time delay and force sensing means have been devised to accomplish delayed separation or ejection; however, they all suffer a common disadvantage in that they necessarily add complexity and expense to the resulting toy.

The present invention relates to the type of projectile discussed above and overcomes the stated disadvantages by providing an elastically propelled multi-stage projectile which accomplishes realistic separation and propulsion of successive stages without the use of time delay or force sensing switches. This is achieved by utilizing the set-back force generated by the initial launch of the booster of the projectile to impart a cocking force in the elastic propulsion means of the succeeding stages. The time delay necessary for realistic separation is achieved in this device by judiciously choosing the relative inertial masses of the various components of the system and elastic properties of the propulsion means to provide real and apparent separation at desired points in the trajectory.

It is therefore an object of this invention to provide a novel and realistic multi-stage toy projectile which is both entertaining and educational.

It is another object of this invention to provide a simple and inexpensive method of separating and propelling the various stages of a multi-stage toy projectile.

It is still another object of this invention to provide a safe and durable multi-stage toy projectile.

It is yet another object of this invention to provide a multi-stage toy rocket simulating projectile which furnishes a maximum amount of realism with a minimum amount of complexity.

Many of the other attendant objects and advantages of this invention will be apparent from the following detailed description, when viewed in light of the accompanying drawings in which:

FIG. 1 is a side view partially in section, of an embodiment of the present invention showing the components of the system assembled for launching;

FIG. 2 is a side View of the embodiment of FIG. 1, showing the components of the system deployed after launching and separation thereof;

FIG. 3 is a transverse section on the line 3-3 of FIG. 1',

FIG. 4 is a transverse section on the line 4-4 of FIG. 1;

FIG. 5 is a transverse section on the line 55 of FIG. 1;

FIG. 6 is a side view of another embodiment of the 3,134,194 Patented May 26., 1964 "ice present invention, showing the components of the system deployed after launching and separation thereof;

FIG. 7 is a fragmentary side view, in section, of the embodiment of FIG. 6;

FIG. 8 is a transverse section on the line 8-8 of FIG. 7; and

FIG. 9 is a side View, partly in section, of another embodiment of the present invention prior to launching.

Referring now to FIGS. 1 through 5, the embodiment is shown in its pro-launching and post-launching dispositions. The system consists of three main components; the launching track 2, the first stage member 4, and the final stage glider 6. The launching track comprises frame member 8, having a pair of upright arms 10. The base 12 is formed to easily penetrate the earth at point 14. Rollers 18 are rotatably fixed to each of arms 10 near the top ends thereof. Launching elastic loop 20 is initially positioned across rollers 18 and down the outer sides of arms 10 in a taut but substantially unstressed condition. Loop 20 is connected at either end around retaining posts 22, which are in turn connected to the sides of arms 10 near the base thereof. Elastic restraining hook member 24 is fixed to a face of the base of frame 8 and is disposed so that hook 26 extends over the slot between the arms at the lower end thereof. Release cord 28 is attached near the mid portion of hook member 24.

First stage member 4 has tubular walls 30 of such diameter as to slidably fit over launching track 2 as shown in FIG. 1. Fin members 32 are disposed across the base of the first stage and have fin projections 34 extending from opposite sides of wall 3. These fin projections provide aerodynamic stability and structural rigidity as well as realistic appearance for first stage member 4. These projectionsmay be of any shape suitable to achieve the above objectives and may take on the character of threedimensional rocket motor housings such as those on the Convair-Atlas booster. Cross pieces 36 of the fin member support base plate member 37. Hook receiving holes 35 are disposed through plate member 37. First stage member 4 is disposed over launching track 2 and, with base plate 37 engaging hook member 26 through one of the holes 35, causing elongating of launching elastic loop 20 over rollers 18 as shown in FIG. 1.

Frusto-conical adapter portion 3 8 is connected to the top of first stage member 4. Guide rails 39 are disposed longitudinally along the walls 30 of first stage member 4 near the top end thereof and extend radially inward as shown. First stage elastic band 40* is connected at either end to opposite sides of adapter 38 near the upper end thereof and is of sufiicient length to be extended in its Enstressed condition into the interior of first stage mem- Glider member 6 has body member 42, empennage 44 and folding wings 46. The wings are connected at their roots to pivot 48 and are biased in an extended position as shown in 'FIG. 2, by elastic extender 50. The leading edge 52 of the wings 46 and the tips of the empennage 44 are formed to slidably fit into tubular walls 30 of first stage 4 when the wings are folded as shown in FIG. 1. Adapter portion 38 is provided with slots 58 to accommodate the folded wings and empennage of the glider. Body member 42 is fitted into the upper end of first stage 4- and is provided with elastic engaging surface 60 at the base thereof. Slots 58 are oriented with respect to first stage elastic member 40' so that surface 60 is guided to engage elastic member 40 at the mid portion thereof. The unstressed elastic member 40 has sufficient slack to (accommodate glider 6 in first stage member 4 in' a partially telescoped relationship therein as shown in FIG. 1. i In operation the system is assembled as shown in FIG. '1.

The projectile is launched in the following manner: release cord 28 is pulled thereby elastically bending hook member 24 to release base plate 37. The elastic loop then contracts, accelerating first stage 4 up track 2. Glider 6, due to its inertia, initially tends to remain in the same position relative to the launching track, causing first stage elastic band 48 to deform, thereby imparting energy therein. As inertia is overcome, glider 6 will be accelerated by the energy in elastic band 41) and propelled from first stage 4. After propulsion from the first stage, glider wings 46 will tend to remain folded until the aerodynamic forces acting thereon diminish. At this point the wings will deploy and the glider will return to the ground in a conventional fashion.

Referring now to FIGS. 6- through 8, another embodiment of the invention is shown. In this embodiment, glider 6 is replaced with a second intermediate stage 62 which has elastic engaging slots 68 and 69' in the lower and upper ends thereof. The intermediate stage is fitted into the upper end of first stage 4 and slidably engages guide rails 39. A hollow capsule third stage member 70, simulating a space capsule such, for example, as the capsule of the Mercury/Atlas system, is disposed over second stage member '62 and is placed on the lower end of adapter 38 of first stage member 4. Third stage member 70 may also have a parachute 72 connected to the top of the capsule. Escape tower 76 is preferably constructed of opaque material with simulated truss members 77 printed or otherwise indicated thereon and serves as a housing for collapsed parachute 72 as shown in FIG. 7. The tower is removably fitted to the top of the capsule and contains the parachute therein. Third stage elastic band 78 is connected at either end to opposite sides of the interior of third stage member 70 near the base thereof. Second stage member 6-2 is so formed as to engage first stage elastic 40 in lower slot 68 at the mid portion of the elastic member and extend the elastic in a taut yet substantially unstressed condition when first stage 4 and third stage 70 are assembled as shown in FIG. 7. Elastic 78 is initially disposed to one side of second stage 62, as shown in FIG. 8.

J'Ihe operation of the embodiment of FIGS. 6 through 8 is as follows: The first stage is launched as in the embodiment of FIGS. 1 through 5. Launching acceleration of the first stage, in combination with the inertia of second stage 62, causes first stage elastic band 40 to deform as described above. Second stage 62 retracts, as shown at 62a in FIG. 7, below third stage elastic 78, allowing it to center thereover. As inertia is overcome, first stage elastic band 40' propels second stage '62 upwardly into third stage 70, separating it from first stage 4. As the second stage is propelled into third stage 70', it also engages third stage elastic band 78, elongating it upwardly and imparting energy therein. When acceleration due to the propulsion from first stage elastic band 40 diminishes, third stage elastic band 78 propels third stage 70 from second stage 62. Escape tower 76 and third stage 70 are so designed with respect to their relative masses, drag areas and frictional connection therebetween, that the drag forces acting thereon Will cause them to separate, exposing parachute 72. Separation of the tower and the third stage thereby causes deployment of parachute 72 and provides parachute descent for the third stage.

:It is intended that the configurations of the payload may be modified to include vehicles of contemporary interest such as ballistic missiles, space gliders, inter-planetary vehicles and the like. The first stage could also be modified to duplicate replicas of contemporary boosters such, for example, as the Atlas, Centaur, Saturn and the like. Multi-stage guided missiles, nested aircraft, aircraft launched missiles or projectiles, and similar systems, may also be simulated utilizing these embodiments of the invention.

Although the embodiments described above show the use of elastic bands for propulsion of the various components, coil springs or the like could be substituted with similar results. Referring now to FIG. 9, coil compression spring 120 is shown disposed in an uncompressed condition within a tubular spring guide 122. The guide is in turn connected by suitable means to first stage Walls 30. A second stage member is shown slidably disposed in the guide 122 on top of the spring. Acceleration of first stage 4 will cause compression of spring 120 due to the inertia of the second stage and, in a manner similar to the embodiments utilizing elastic band, will subsequently propel stage 80 from member 4.

It is also contemplated that the launching system could be enclosed in separate structures, formed to simulate realistic launch-complex equipment such as gantry towers or the like and disposed adjacent tothe missile to accomplish the launch. These systems would allow the use of higher energy springs or elastic bands since they would not have the size limitation imposed by the space available for systems integrally disposed in the missile. Referring again to FIG. 9, a generalized example of the above system is shown. Tubular gantry tower is fixed at one end to platform H92 and is closed at the other by wall 103. Longitudinal slot 101 is provided through the wall of tower 100. Compression spring 104 is coaxially disposed in the base of the tube and cylindrical spring follower 106 rides thereon. Arm 109 extends through slot 101 connecting launching pallet 168 to follower 106. Elastic trigger 110 is connected at the base of tower 1% and extends through opening 112 to engage follower 106 and retain it in a cocked position. Trigger cord 114 is connected near the, top of the trigger.

To operate this example of the launcher, the mechanism is cocked by depressing pallet 108 until trigger 110 engages follower 106. The assembled missile is then placed on the pallet. Launching is accomplished through elastically deflecting trigger 110 by tension on cord 114, thereby disengaging follower 106 and allowing spring 104 to expand. The follower accelerates pallet 108 and the missile upwardly until it is stopped by wall 103. The missile then continues in the manner heretofore described. The pallet may be provided with guide members 118 which are formed with fin slots to slidably receive the base of the missile thereby stabilizing it during launching.

FIG. 9 further shows one of the payload modifications referred to above. A second stage missile 80 is shown mounted in first stage 4 with fins 96 disposed in slots 58. To increase realism the missile may also be provided With an impact actuated percussion cap and detonating means, such as relatively movable nose and body sections.

In operation, the stages are assembled as described above and the projectile is launched and deployed as described above. Missile 80 follows a typical ballastic trajectory after separation from second stage 62 and, upon impact, the cap is exploded.

Of course, non-explosive noise making devices such as diaphragms alone or mouse trap type snappers may be substituted for the cap with a similar effect. It is also contemplated that the missile may incorporate smoke making devices or be formed to segment or fly apart on impact to add realism to the Warhead.

It is intended that the major components of the projec* tile itself will be made of a rigidized or reinforced plastic material such as rigid vinyl or the like. The elastic propulsive members may be made from elastomeric material suitable for the purpose or, in the case of metal springs, suitable spring steel. The members may be in the form of bands, coils, strips, tubes or the like. Although the launching means may be made of rigidized plastic, they could also be fabricated from a a metal or wood.

The launching means described above are shown solely to illustrate examples utilizing the invention and could be replaced by other systems such as hand held launchers, sling shots or the like.

Obviously many other modifications and variations of the present invention are possible in the light of the posed in succeeding relationship,

above teachings. It is therefore to be understood that, within the scope of the attendant claims, the invention may be practiced otherwise than specifically described.

What is claimed as new and desired to be secured by Letters Patent of the United States is:

l. A multi-stage aerial toy adapted to separate in flight comprising a plurality of separable members disposed in succeeding telescopicable relationship, said members being initially disposed in a partially telescoped relationship, means between the launching-end member and the succeding stages thereto to absorb and retain a portion of the energy of launching for imparting delayed relative motion to said succeeding stages, means between each of said succeeding stages to absorb and retain a portion of the energy from the impartation of said relative motion for sequentially imparting delayed relative motion to the succeeding stages thereto, whereby substantial telescoping of said members occurs under the inertial load of said members when said toy is accelerated in launching and whereby telescoping of said members imparts energy into said second and fourth mentioned means to provide successive separation and propulsion of said members with respect to one another when the launching acceleration has diminished.

2. A toy in accordance with claim 1, wherein each of said members is formed so that the succeeding stage thereto is telescopically slidable therein.

3. A toy in accordance with claim 31, wherein an intermediate stage of said members is formed to telescope into the preceeding and succeeding stage thereto.

4. A toy in accordance with claim 1, wherein the last separated member thereof comprises a space craft simulating vehicle, a parachute in said vehicle disposed to be deployed after separation from said toy.

5. A multi-stage aerial toy adapted to be separated in flight comprising a plurality of separable members diseach of said members formed to telescopically receive a succeeding member thereto, said members being intially disposed in a partially telescoped relationship, means between the launchingend member and the succeeding stages thereto to absorb and retain a portion of the energy of launching for imparting delayed relative motion to said succeeding stages, means between each of said succeeding stages to absorb and retain a portion of the energy from the impartation of said relative motion for sequentially imparting delayed relative motion to the succeeding stages thereto, whereby impartation of energy into said means upon launching of said toy provides energy therein to successfully separate and propel said members with respect to one another when the launching acceleration has diminished.

6. A multi-stage aerial toy adapted to be separated in flight comprising a launcher, a tubular first-stage member slidable on said launcher, a retaining means releasably connecting said first stage member to said launcher, a stressed first elastic means in said launcher to propel said first stage, a tubular second stage member telescopically slidable on said first stage member and disposed in a partially telescoped condition thereon, a second elastic means to absorb and retain a portion of the energy from said launcher for imparting relative motion to said second stage, whereby propulsion of said first stage member from a launcher causes said second stage member to telescopically retract onto said first stage member thereby imparting energy into said second elastic means, and whereby said second elastic means propels said second stage memstage member is telescopically slida-ble on said second stage member and disposed in a partially telescoped condition thereon, a third elastic means to absorb and retain a portion of the energy from the impantation of relative motion from said second elastic means for imparting relative motion to said third stage member, whereby propulsion of said first and second stage members from a launcher causes said third stage member to telescopically retract into said second stage member thereby imparting energy into said third elastic means and whereby propulsion of said second stage member from said first stage member causes said third stage member to remain retracted in said second stage member due to the intial load of said third stage member under the influence of acceleration of said second stage member, and whereby said third elastic means propels said third stage member from said second stage member when said initial load of said third stage member has diminished.

8. In a multi-stage aerial toy adapted to be separated in flight, a plurality of telescopicable tubular stages disposed in a partially telescoped condition, a coil spring member coaxially disposed in the launching-end stage and fixed at one end thereto to absorb and retain through deformation thereof a portion of the energy from said launching means for imparting relative motion to the succeeding stages thereto, a coil spring member coaxially disposed in each of said succeeding stages to absorb and retain a portion of the energy from the impartation of said relative motion for sequentially imparting delayed relative motion to the succeeding stages thereto, whereby said springs propel said succeeding stages with respect to one another when said launching acceleration has diminished.

9. In a multi-stage aerial toy adapted to be separated in flight, a plurality of telescopicable tubular stages disposed in -a partially telescoped condition, an elongated elastic member diametrically disposed across the upper end of the launching-end stage to absorb and retain a portion of the energy from a launching means for imparting relative motion to the succeeding stages thereto, an elongated elastic member diametrically disposed across the upper end of each of said succeeding stages to absorb and retain a portion of the energy from the impartation of said relative motion for sequentially imparting delayed relative motion to the succeeding stages thereto, whereby said elongated elastic members propel said stages with respect to one another when said launching acceleration has diminished.

References Cited in the file of this patent UNITED STATES PATENTS 1,565,437 Greife Dec. 15, 1925 2,663,291 Hall Dec. 22, 1953 2,923,089 Fissel Feb. 2, 1960 3,084,476 Sunray Apr. 9, 1963 3,085,363 Sunray Apr. 16, 1963 FOREIGN PATENTS 31,213,068 France Oct. 26, 1959 1,236,097 I France June 7, 1960 

1. A MULTI-STAGE AERIAL TOY ADAPTED TO SEPARATE IN FLIGHT COMPRISING A PLURALITY OF SEPARABLE MEMBERS DISPOSED IN SUCCEEDING TELESCOPICABLE RELATIONSHIP, SAID MEMBERS BEING INITIALLY DISPOSED IN A PARTIALLY TELESCOPED RELATIONSHIP, MEANS BETWEEN THE LAUNCHING-END MEMBER AND THE SUCCEDING STAGES THERETO TO ABSORB AND RETAIN A PORTION OF THE ENERGY OF LAUNCHING FOR IMPARTING DELAYED RELATIVE MOTION TO SAID SUCCEEDING STAGES, MEANS BETWEEN EACH OF SAID SUCCEEDING STAGES TO ABSORB AND RETAIN A PORTION OF THE ENERGY FROM THE IMPARTATION OF SAID RELATIVE MOTION FOR SEQUENTIALLY IMPARTING DELAYED RELATIVE MOTION TO THE SUCCEEDING STAGES THERETO, WHEREBY SUBSTANTIAL TELESCOPING OF SAID MEMBERS OCCURS UNDER THE INERTIAL LOAD OF SAID MEMBERS WHEN SAID TOY IS ACCELERATED IN LAUNCHING AND WHEREBY TELESCOPING OF SAID MEMBERS IMPARTS ENERGY INTO SAID SECOND AND FOURTH MENTIONED MEANS TO PROVIDE SUCCESSIVE SEPARATION AND PROPULSION OF SAID MEMBERS WITH RESPECT TO ONE ANOTHER WHEN THE LAUNCHING ACCELERATION HAS DIMINISHED. 